Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database search

Search the 1638 airfoils available in the databases filtering by name, thickness and camber. Click on an airfoil image to display a larger preview picture. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.

(coanda2-il) Coanda 2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Coanda 2 airfoil Max thickness 6% at 30% chord Max camber 2.9% at 30% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(clarkw-il) CLARK W AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK W airfoil Max thickness 11.2% at 30% chord Max camber 3.7% at 40% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe593-il) GOE 593 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 593 airfoil Max thickness 11.9% at 30% chord Max camber 4.1% at 40% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e556-il) EPPLER 556 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E556 general aviation airfoil Max thickness 16% at 31.1% chord Max camber 3.1% at 61.4% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(l188tip-il) LOCKHEED L-188 TIP AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed L-188/P-3 tip airfoil NACA 0012 -1.10 40/1.051 Cli=.4 a=.8 Max thickness 12% at 41.3% chord Max camber 2.7% at 51.7% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(usnps4-il) USNPS4 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Jacobs USNPS4 (smoothed) 17.5 kW wind turbine airfoil Max thickness 11.9% at 34.2% chord Max camber 5% at 34.2% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag26-il) AG26 Bubble Dancer DLG by Mark Drela		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG26 airfoil used on the Bubble Dancer R/C DLG Max thickness 6.8% at 23.3% chord Max camber 2.5% at 45.5% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe440-il) GOE 440 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 440 airfoil Max thickness 15.3% at 30% chord Max camber 9.7% at 40% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe550-il) GOE 550 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 550 airfoil Max thickness 13% at 20% chord Max camber 4.3% at 50% chord Max Cl/Cd 53.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe652-il) GOE 652 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 652 airfoil Max thickness 17.1% at 20% chord Max camber 9.3% at 50% chord Max Cl/Cd 53.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database